公开(公告)号：US20230182918A1

公开(公告)日：2023-06-15

申请号：US17988538

申请日：2022-11-16

Applicant: ROLLS-ROYCE plc

Inventor： Gareth E MOORE ,  Paul R DAVIES ,  Stephen M HUSBAND ,  David R TRAINER ,  David P SCOTHERN ,  Luke GEORGE ,  Douglas M M HERBERT

IPC: B64D31/06 ,  B64D27/24 ,  F01D15/10 ,  B64D27/10

CPC classification number: B64D31/06 ,  B64D27/24 ,  F01D15/10 ,  B64D27/10 ,  B64D2027/026

Abstract: Aircraft power and propulsion systems and methods of operating the systems, one method includes: operating electric machines of gas turbine engines as generators to extract mechanical power from spools and generating electrical power therefrom; meeting an electrical power demand of a plurality of electrical loads connected with an electrical system by supplying the plurality of electrical loads with electrical power generated by the electric machines; determining when there is an electrical system and/or the gas turbine engine fault and an amount of electrical power generated by the power and propulsion system is reduced to a lower level; and responsive to the determination: during a time period ΔT, controlling the plurality of electrical loads reducing the electrical power demand; and during the time period ΔT, meeting at least part of the electrical power demand of the plurality of electrical loads by discharging the electrical energy storage system.

公开(公告)号：US20230167785A1

公开(公告)日：2023-06-01

申请号：US17940421

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Paul R DAVIES ,  Gareth E MOORE ,  Stephen M HUSBAND ,  David R TRAINER ,  David P SCOTHERN ,  Luke GEORGE

IPC: F02K3/06 ,  F01D15/10

CPC classification number: F02K3/06 ,  F01D15/10 ,  F05D2220/36 ,  F05D2220/323

Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum dry thrust T (N); and a ratio S of:


S=(Maximum Electrical Power Generated=PEM1)/(Maximum Dry Thrust=T)

is in a range of between 2.0 and 10.0.

公开(公告)号：US20230182920A1

公开(公告)日：2023-06-15

申请号：US17988341

申请日：2022-11-16

Applicant: ROLLS-ROYCE plc

Inventor： Gareth E MOORE ,  Paul R DAVIES ,  Stephen M HUSBAND ,  David R TRAINER ,  David P SCOTHERN ,  Luke GEORGE ,  Douglas M M HERBERT

IPC: B64D35/02 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06

CPC classification number: B64D35/02 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  B64D2027/026

Abstract: A twin-engine aircraft power and propulsion system including first and second propulsive gas turbine engines, each having combustion equipment and a first and second spool; first, second, third, and fourth electrical power generation sub-systems including electric machines respectively mechanically coupled with the first spool of the first propulsive gas turbine engine, the second spool of the first propulsive gas turbine engine, the first spool of the second propulsive gas turbine engine, and the second spool of the second propulsive gas turbine engine; and first, second, third, and fourth power channels respectively connected with distribution sides of the first electric machine, second electric machine, third electric machine, and fourth electric machine.

公开(公告)号：US20180016935A1

公开(公告)日：2018-01-18

申请号：US15637000

申请日：2017-06-29

Applicant: ROLLS-ROYCE PLC

Inventor： David P SCOTHERN

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2220/32 ,  F05D2260/80 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/54 ,  F05D2270/808 ,  G01K13/02 ,  G01K15/007 ,  G01K2013/024 ,  G01K2205/00 ,  G01L27/002 ,  G01L27/007

Abstract: A method of determining a faulty sensor of a sensor array of a gas turbine engine (10), the sensor array comprising at least first, second and third sensors (A, B, C), the method comprising the steps of: a. measuring a first set of sensor outputs (S1A, S1B, S1C) prior to engine startup from each sensor (A, B, C), and calculating a first difference (S1A-S1B, S1A-S1C, S1B-S1C) in the measured value for each sensor pair (A; B, A;C, B;C); b. after a period of time, measuring a second set of sensor outputs (S2A, S2B, S2C) prior to engine startup from each sensor (A, B, C), and calculating a second difference (S2A-S2B, S2A-S2C, S2B-S2C) in measured value for each sensor pair (A;B, A;C, B;C); c. calculating a further difference ((S1A-S1B) -(S2A-S2B), (S1A-S1C)-(S2A-S2C), (S1B-S1C)-(S2B-S2C)) between the calculated first and second differences for each sensor pair (A; B, A;C, B;C); and d. identifying a failed sensor (A, B, C) where two or more sensor pairs (A;B, A;C, B;C) comprising a common sensor (A, B, C) have a further difference above a predetermined threshold.